EP 1801347 A2 20070627 - High pressure turbine disk hub with curved hub surface and method
Title (en)
High pressure turbine disk hub with curved hub surface and method
Title (de)
Hochdruckturbinenscheibennabe mit gekrümmter Nabenoberfläche und Verfahren
Title (fr)
Moyeu de papillon de turbine haute pression avec une surface de moyeu incurvée et procédé
Publication
Application
Priority
US 30622705 A 20051220
Abstract (en)
A first stage turbine disk (14) for a gas turbine engine, including a centrally disposed disk hub (21) having an integrally-formed, radially outwardly extending web (18) terminating at an outer end. The disk hub (21) has a convex, curved hub surface (22) exposed to high pressure, high temperature compressor bleed and discharge gases during engine operation, and the convex, curved hub surface (22) acts to reduce the axial constraint at the location of peak axial stress, thereby mitigating the formation of undesirable axial stress in the disk hub (21) and allows separation of the peak axial and hoop stresses, thereby reducing the magnitude of the peak hub surface effective stress.
IPC 8 full level
F01D 5/00 (2006.01); F01D 5/02 (2006.01); F01D 5/06 (2006.01); F01D 5/08 (2006.01); F01D 5/30 (2006.01)
CPC (source: EP US)
F01D 5/00 (2013.01 - EP US); F01D 5/02 (2013.01 - EP US); F01D 5/06 (2013.01 - EP US); F01D 5/08 (2013.01 - EP US); F01D 5/30 (2013.01 - EP US); Y02T 50/60 (2013.01 - EP US)
Designated contracting state (EPC)
DE FR GB
Designated extension state (EPC)
AL BA HR MK RS
DOCDB simple family (publication)
EP 1801347 A2 20070627; EP 1801347 A3 20140514; EP 1801347 B1 20170222; CN 1995707 A 20070711; CN 1995707 B 20110608; JP 2007170389 A 20070705; JP 5289704 B2 20130911; US 2007140856 A1 20070621; US 7458774 B2 20081202
DOCDB simple family (application)
EP 06126601 A 20061220; CN 200610169096 A 20061220; JP 2006342779 A 20061220; US 30622705 A 20051220